The invention discloses a resistance and heat reduction structure for hypersonic flight of a blunt forebody aircraft, and belongs to the field of aerodynamic resistance and heat reduction of hypersonic aircrafts. The device comprises a pneumatic disc expansion half-angle section, a pneumatic disc, a shock wave needle, a flow channel, a blunt precursor and a jet flow working medium inlet, the flow channel comprises a reverse flow guide channel, a throttling control section, a blunt front body wall surface flow guide channel and a blunt front body wall surface jet flow outlet section; the blunt precursor includes a blunt precursor upstream portion and a blunt precursor downstream portion. The blunt front body wall surface flow guide channel is a ball-head-shaped empty groove covering the upstream part of the blunt front body; and the jet outlet section of the blunt front body wall surface is an annular nozzle. The jet cooling working medium is sprayed out from the jet working medium inlet and flows from right to left. And when flowing through the throttling control section, the jet cooling working medium is shunted, one part flows to the reverse flow guide channel, and the other part flows to the blunt front body wall surface flow guide channel. The shock wave needle and the jet flow are combined, the blunt precursor is protected through the pneumatic disc, the shock wave needle, the flow channel and the jet flow, and the resistance reduction and heat reduction efficiency is improved.

    本发明公开的一种钝前体飞行器高超声速飞行降阻减热结构,属于高超声速飞行器气动降阻减热领域。本发明包括气动盘膨胀半角段、气动盘、激波针、流道、钝前体和射流工质入口;流道包括逆向导流道、节流控制段、钝前体壁面导流道、钝前体壁面射流出口段;钝前体包括钝前体上游部分和钝前体下游部分。钝前体壁面导流道为覆盖钝前体上游部分的球头型空槽;钝前体壁面射流出口段为环形喷口。射流冷却工质从射流工质入口喷出,冷却工质从右向左流动。流经节流控制段时射流冷却工质进行分流,一部分流向逆向导流道,其余部分流向钝前体壁面导流道。本发明将激波针和射流相结合,采用气动盘、激波针、流道和射流对钝前体进行保护,提高降阻减热的效率。


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    Title :

    Hypersonic flight resistance-reducing and heat-reducing structure of blunt-forebody aircraft


    Additional title:

    一种钝前体飞行器高超声速飞行降阻减热结构


    Contributors:
    LONG TENG (author) / WANG ZIYU (author) / ZHANG BAOSHOU (author) / SHI RENHE (author) / ZHANG YAO (author) / LI HAODA (author)

    Publication date :

    2024-09-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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